THE NEXT GENERATION OF INTELLIGENT AEROSPACE VEHICLES WILL BE ABLE TO FEEL THINK AND REACT IN REAL TIME BASED ON HIGH RESOLUTION STATE SENSING CAPABILITIES AND DATA DRIVEN METHODS FOR STRUCTURAL AND FLIGHT STATE AWARENESS. SUCH VEHICLES WILL BE ABLE TO SENSE THE ENVIRONMENT TEMPERATURE AMBIENT AIR PRESSURE ETC. SENSE THEIR FLIGHT VIBRATION FLUTTER STALL AERODYNAMIC LOADS ETC. AND STRUCTURAL HEALTH STATE DETECT LOCALIZE AND QUANTIFY DAMAGE AND EFFECTIVELY INTERPRET THE SENSING DATA TO ACHIEVE REALTIMESTATE AWARENESS AND IMPROVE THE VEHICLE PERFORMANCE AND CONTROL CHARACTERISTICS.IN THIS PROJECT STANFORD UNIVERSITY WILL ADDRESS THE DESIGN AND INTEGRATION OF A SELF SENSING SMART WING WITH EMBEDDED DISTRIBUTED SENSOR NETWORKS AND PERFORM THE WIND TUNNEL EXPERIMENTAL ASSESSMENT BASED ON DATA STRAIN TEMPERATURE AND VIBRATION DATA COLLECTED UNDER VARYING FLIGHT CONDITIONS SUCH AS AIRSPEED AND ANGLE OF ATTACK. THE PROPOSED WING DESIGN INCORPORATES NOVEL BIO-INSPIRED MULTI MODAL SENSOR NETWORKS THAT CAN BE EMBEDDED INSIDE COMPOSITE MATERIALS TO PROVIDE BUILT IN SENSING AND INTELLIGENCE CAPABILITIES TO VARIOUS STRUCTURAL COMPONENTS SUCH AS WINGS FUSELAGE AND OTHER CRITICAL COMPONENTS. MICRO FABRICATED STRETCHABLE SENSOR NETWORKS INCLUDING INTEGRATED PIEZOELECTRIC STRAIN AND TEMPERATURE SENSORS WILL BE DESIGNED AND MONOLITHICALLY EMBEDDED IN THE LAYUP OF THE COMPOSITE WING IN ORDER TO PROVIDE THE SELFSENSINGCAPABILITIES. THE WING WILL BE ABLE TO SENSE ITS STRUCTURAL STATE AND SURROUNDING ENVIRONMENT DURING FLIGHT AND INTERPRET THE SENSING INFORMATION IN ORDER TO DETERMINE ITS ACTUAL OPERATING STATE AND FLIGHT CONFIGURATION. STRAIN GAUGES WILL BE USED TO DETERMINE THE STRAIN DISTRIBUTION AND LOADING CONDITIONS AND IDENTIFY POTENTIAL CRITICAL STRUCTURAL AREAS FOR THE CONSIDERED EXPERIMENTAL CONDITIONS. PIEZOELECTRIC SENSORS WILL BE USED TO SENSE THE VIBRATION OF THE WING IN ORDER TO IDENTIFY AND MONITOR THE COUPLED AIRFLOW STRUCTURAL DYNAMICS. THE RECORDED DATA WILL BE ANALYZED AT STANFORD UNIVERSITY AND NASA LANGLEY CENTER IN ORDER TO PROVE THE FEASIBILITY OF THE DIGITAL TWIN CONCEPT FOR AEROSPACE VEHICLES VIA THE USE OF INTEGRATED REAL-TIME DATA DRIVEN AND PHYSICS BASED APPROACHES.